Expermental investigation on aircraft-store compatibility and flow control for internal weapons separation

SONG Wei; AI Bangcheng

doi:10.7638/kqdlxxb-2021.0258

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Expermental investigation on aircraft-store compatibility and flow control for internal weapons separation

更新时间：2026-05-28

- Expermental investigation on aircraft-store compatibility and flow control for internal weapons separation
- Vol. 40, Issue 3, Pages: 203-211(2022)
- 作者机构：
  
  中国航天空气动力技术研究院空气动力科学中心,北京,100074
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0258
  CLC： V211.7;V212.1
- Published：2022
- 稿件说明：
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宋威, 艾邦成. 内埋武器机弹分离相容性及流动控制试验研究[J]. 空气动力学学报, 2022, 40(3): 203−211.

SONG Wei, AI Bangcheng. Expermental investigation on aircraft-store compatibility and flow control for internal weapons separation[J]. 2022, 40(3): 203-211.
宋威, 艾邦成. 内埋武器机弹分离相容性及流动控制试验研究[J]. 空气动力学学报, 2022, 40(3): 203−211. DOI： 10.7638/kqdlxxb-2021.0258

SONG Wei, AI Bangcheng. Expermental investigation on aircraft-store compatibility and flow control for internal weapons separation[J]. 2022, 40(3): 203-211. DOI： 10.7638/kqdlxxb-2021.0258.

摘要

随着新一代先进有人或无人战斗机对高机动、超远程打击和隐身等性能提出要求，武器内埋式装载已成为必备选择。当内埋武器的质量-惯性载荷比非定常空气动力载荷大时，有效的武器分离通常不是问题；然而，当内埋武器的质量-惯性载荷比非定常空气动力载荷小时，可能导致内埋武器机弹分离过程出现俯仰角过大、急速滚转等不相容现象。本文针对内埋武器机弹分离相容性及流动控制方法开展非定常风洞投放试验探索研究，通过在武器舱前缘布置锯齿和矩形扰流板等被动流动控制装置，采用非定常风洞投放试验方法并结合高速纹影流动显示技术，研究了有无流动装置对内埋武器机弹分离相容性的影响，并提出细长旋成体布局式的内埋武器机弹分离相容性的判据表达式。研究发现，布置在内埋武器舱前缘的锯齿和平顶扰流板能在气流扇形膨胀区域内产生扰流激波，该扰流激波所产生的高压作用在导弹头部能起到减小抬头俯仰力矩的效果，对机弹分离俯仰方向运动产生较大影响，但对导弹垂直位移的影响并不大。前缘锯齿扰流板对机弹分离相容性的控制效果比平顶扰流板要好。

Abstract

With the performance requirements for high maneuverability

ultra-long-range strike and stealth of the new-generation advanced manned or unmanned combat-aircraft

the loading of internal weapons has become a necessary choice. When the mass-inertia load of the internal weapons is larger than the unsteady aerodynamic load

effective weapon separation is usually not a problem. However

when the mass-inertia load of the internal weapons is smaller than the unsteady aerodynamic load

it may lead to incompatible separation phenomenon

such as exc

essive pitch angle and rapid rolling in the aircraft-store separation. In this paper

the exploratory wind tunnel freedrop testing is carried out on the aircraft-store compatibility and flow control for the internal weapons separation. Passive flow control devices

such as sawtooth and flat-top spoilers

are arranged at the leading-edge of weapons bay and the influence of flow devices on internal weapons separation is studied by using the unsteady drop testing method combined with high-speed Schlieren technology in the high-speed wind tunnel. The criterion expression of aircraft-store separation compatibility of the internal weapons which have slender and rotational body is proposed. It is found that the leading-edge sawtooth and flat-top spoilers can generate spoiler shock-wave in the expansion region

which generates the high pressure on the store head reducing pitching moment. The leading-edge spoilers cannot affect the vertical positions

whereas it so greatly affected the pitch-angle (

$\theta $

img text_id='M1' class='formula-img' style='display:none;' src='2021-258_M1.jpg'>

) motion of the store. The effect of flow control of sawtooth spoiler (STS) on the aircraft-store compatibility of the internal store separation is better than that of flat-top spoiler (FTS).

关键词

Keywords

references

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